PORTABLE AIR DEFENSE GROUND BASED LAUNCH DETECTION SYSTEM

• US 20060284050A1
• Filed: 03/02/2005
• Published: 12/21/2006
• Est. Priority Date: 03/02/2005
• Status: Active Grant

• Current Assignee: the united states of america as represented by the secretary of the navy
• Original Assignee: the united states of america as represented by the secretary of the navy
• Inventors: Allen, Jason R., Barrett, Michael D., Boyd, Mallory J., Busse, Richard J., Ditzler, William R., Blattel, Raymond J.
• Granted Patent: US 7,230,221 B2
• Time in Patent Office: Days
• US Class Current: 250/203.100
• CPC Class Codes: G01J 1/4228 arrangements with two or more detectors, e.g. for sensitivity compensation
• CPC Class Codes: G01S 3/783 using amplitude comparison of signals derived from static detectors or detector systems
• CPC Class Codes: G01S 5/16 using electromagnetic waves other than radio waves

Abstract

A ground based launch detection system consisting of a sensor grid of electro-optical sensors for detecting the launch of a threat missile which targets commercial aircraft in proximity to a commercial airport or airfield. The electro-optical sensors are configured in a wireless network which broadcast threat lines to neighboring sensors with overlapping field of views. When a threat missile is verified, threat data is sent to a centrally located processing facility which determines which aircraft in the vicinity are targets and send a dispense countermeasure signal to the aircraft.

Claims

1. A method for protecting aircraft from being attacked by a missile which is launched in proximity to a flight path at an airport comprising the steps of:

(a) detecting the launch of said missile which is targeted at said aircraft traveling along the flight path at said airport;

(b) monitoring said missile as said missile travels towards a targeted aircraft on an intercept path with said targeted aircraft;

(c) generating sensor video of the launch and flight of said missile as said missile travels towards the targeted aircraft on said intercept path, wherein a plurality of electro-optical sensors forming a grid are positioned in proximity to said flight path to generate said sensor video;

(d) processing said sensor video utilizing a plurality of digital computers, one of said digital computers being associated with and connected to one of said plurality electro-optical sensors to receive and process said sensor video generated by said electro-optical sensor;

(e) comparing pixels within said senor video to determine which of said pixels exceed an intensity threshold and then finding a centroid for groups of adjacent pixels which exceed said intensity threshold, said centroid for each of said groups of adjacent pixels being representative of current position coordinates for said missile on said intercept path;

(f) generating sight line data for each of said plurality of electro-optical sensors, said sight line data being generated by processing said centroid for each of said groups of adjacent pixels, said sign line data generated for each of said plurality of electro-optical sensors representing sight lines between said missile and each of said plurality of electro-optical sensors as said missile travels along said intercept path;

(g) broadcasting said sight line data over said grid to each of said digital computers within said grid;

(h) processing said sight line data to determine when one of said sight lines intersects with another of said sight lines for a pair of electro-optical sensors having overlapping field of views wherein said digital computers within said grid process said sight line data to find each intersection of sight lines of said electro-optical sensors having overlapping field of views;

(i) generating three dimensional X,Y,Z coordinates of a point along the intercept path of said missile whenever one of said sight lines intersects with another of said sight lines for said pair of electro-optical sensors having overlapping field of views and an observation time for said three dimensional x,y,z coordinates wherein each of said digital computers within said grid generate said three dimensional X,Y,Z coordinates;

(j) transmitting said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to a central processor;

(k) correlating said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to generate a velocity vector which discriminates missile trajectory from infrared emissions in proximity to said missile; and

(l) identifying which of said aircraft on the flight path at said airport are target aircraft of said missile.

2. The method of claim 1 further comprising the step of sending a dispense countermeasure signal to said target aircraft, wherein an antenna connected to said central processor transmits said dispense countermeasure signal to said target aircraft via an RF (radio frequency) link.

3. The method of claim 2 wherein said target aircraft upon receiving said dispense countermeasure signal releases a countermeasure to deceive said missile and re-route said missile from said flight path.

4. The method of claim 1 wherein approximately one half of said electro-optical sensors within said grid are positioned on one side of said flight path equidistant from one another, and the other half of said electro-optical sensors within said grid are positioned on the opposite side of said flight path equidistant from one another, wherein said electro-optical sensors adjacent to one another have said overlapping field of views.

5. The method of claim 1 each of said electro-optical sensors within said grid comprises an indium antimonide (InSb) detector operating in a medium IR band.

6. The method of claim 5 wherein said indium antimonide (InSb) detector is a cryogenically cooled detector.

7. The method of claim 1 wherein said sensor video is processed frame by frame by each of said digital computers locally since there are network bandwidth limitations for said grid.

8. The method of claim 1 wherein a Kalman filter generates said velocity vector which discriminates said missile trajectory from said infrared emissions in proximity to said missile.

9. The method of claim 1 wherein said grid comprises twelve electro-optical sensors spaced apart by approximately twenty kilometers to provide missile threat detection capability over a distance of approximately one hundred kilometers, six of said twelve electro-optical sensors being positioned approximately parallel to said flight path on one side of said flight path and six of said twelve electro-optical sensors being positioned approximately parallel to said flight path on the other side of said flight path.

10. The method of claim 1 wherein each of said digital computers within said grid includes a video monitor connected to said digital computer and an antenna connected to said digital computer, said antenna providing for communications within said grid including the step of broadcasting said sight line data over said grid.

11. The method of claim 1 wherein each of said plurality of digital computers comprises a personal computer having a windows operating system.

12. A method for protecting aircraft from being attacked by a missile which is launched in proximity to a flight path at an airport comprising the steps of:

(a) detecting the launch of said missile which is targeted at said aircraft traveling along the flight path at said airport;

(b) monitoring said missile as said missile travels towards a targeted aircraft on an intercept path with said targeted aircraft;

(c) generating sensor video of the launch and flight of said missile as said missile travels towards the targeted aircraft on said intercept path, wherein a plurality of electro-optical sensors forming a grid are positioned in proximity to said flight path to generate said sensor video;

(d) processing said sensor video utilizing a plurality of digital computers, one of said digital computers being associated with and connected to one of said plurality electro-optical sensors to receive and process said sensor video generated by said electro-optical sensor;

(e) comparing pixels within said senor video to determine which of said pixels exceed an intensity threshold and then finding a centroid for groups of adjacent pixels which exceed said intensity threshold, said centroid for each of said groups of adjacent pixels being representative of current position coordinates for said missile on said intercept path;

(f) generating sight line data for each of said plurality of electro-optical sensors, said sight line data being generated by processing said centroid for each of said groups of adjacent pixels, said sign line data generated for each of said plurality of electro-optical sensors representing sight lines between said missile and each of said plurality of electro-optical sensors as said missile travels along said intercept path;

(g) broadcasting said sight line data over said grid to each of said digital computers within said grid;

(h) processing said sight line data to determine when one of said sight lines intersects with another of said sight lines for a pair of electro-optical sensors having overlapping field of views wherein said digital computers within said grid process said sight line data to find each intersection of sight lines of said electro-optical sensors having overlapping field of views;

(i) generating three dimensional X,Y,Z coordinates of a point along the intercept path of said missile whenever one of said sight lines intersects with another of said sight lines for said pair of electro-optical sensors having overlapping field of views and an observation time for said three dimensional x,y,z coordinates wherein each of said digital computers within said grid generate said three dimensional X,Y,Z coordinates;

(j) transmitting said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to a central processor;

(k) correlating said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to generate a velocity vector which discriminates missile trajectory from infrared emissions in proximity to said missile;

(l) identifying which of said aircraft on the flight path at said airport are target aircraft of said missile; and

(m) sending a dispense countermeasure signal to said target aircraft, wherein said target aircraft upon receiving said dispense countermeasure signal releases a countermeasure comprising an infrared flare to deceive said missile and re-route said missile from said flight path.

13. The method of claim 12 wherein approximately one half of said electro-optical sensors within said grid are positioned on one side of said flight path equidistant from one another, and the other half of said electro-optical sensors within said grid are positioned on the opposite side of said flight path equidistant from one another, wherein said electro-optical sensors adjacent to one another have said overlapping field of views.

14. The method of claim 13 each of said electro-optical sensors within said grid comprises an indium antimonide (InSb) detector operating in a medium IR band.

15. The method of claim 14 wherein said indium antimonide (InSb) detector is a cryogenically cooled detector.

16. The method of claim 12 wherein said sensor video is processed frame by frame by each of said digital computers locally since there are network bandwidth limitations for said grid.

17. The method of claim 12 wherein a Kalman filter generates said velocity vector which discriminates said missile trajectory from said infrared emissions in proximity to said missile.

18. The method of claim 12 wherein said grid comprises twelve electro-optical sensors spaced apart by approximately twenty kilometers to provide missile threat detection capability over a distance of approximately one hundred kilometers, six of said twelve electro-optical sensors being positioned approximately parallel to said flight path on one side of said flight path and six of said twelve electro-optical sensors being positioned approximately parallel to said flight path on the other side of said flight path.

19. The method of claim 12 wherein each of said digital computers within said grid includes a video monitor connected to said digital computer and an antenna connected to said digital computer, said antenna providing for communications within said grid including the step of broadcasting said sight line data over said grid.

20. A method for protecting aircraft from being attacked by a missile which is launched in proximity to a flight path at an airport comprising the steps of:

(a) detecting the launch of said missile which is targeted at said aircraft traveling along the flight path at said airport;

(b) monitoring said missile as said missile travels towards a targeted aircraft on an intercept path with said targeted aircraft;

(c) generating sensor video of the launch and flight of said missile as said missile travels towards the targeted aircraft on said intercept path, wherein a plurality of electro-optical sensors forming a grid are positioned in proximity to said flight path to generate said sensor video, one half of said electro-optical sensors within said grid are positioned on one side of said flight path equidistant from one another, and the other half of said electro-optical sensors within said grid are positioned on the opposite side of said flight path equidistant from one another, said electro-optical sensors adjacent to one another having said overlapping field of views;

(d) processing said sensor video utilizing a plurality of digital computers, one of said digital computers being associated with and connected to one of said plurality electro-optical sensors to receive and process said sensor video generated by said electro-optical sensor;

(e) comparing pixels within said senor video to determine which of said pixels exceed an intensity threshold and then finding a centroid for groups of adjacent pixels which exceed said intensity threshold, said centroid for each of said groups of adjacent pixels being representative of current position coordinates for said missile on said intercept path;

(f) generating sight line data for each of said plurality of electro-optical sensors, said sight line data being generated by processing said centroid for each of said groups of adjacent pixels, said sign line data generated for each of said plurality of electro-optical sensors representing sight lines between said missile and each of said plurality of electro-optical sensors as said missile travels along said intercept path;

(g) broadcasting said sight line data over said grid to each of said digital computers within said grid;

(h) processing said sight line data to determine when one of said sight lines intersects with another of said sight lines for a pair of electro-optical sensors having overlapping field of views wherein said digital computers within said grid process said sight line data to find each intersection of sight lines of said electro-optical sensors having overlapping field of views;

(i) generating three dimensional X,Y,Z coordinates of a point along the intercept path of said missile whenever one of said sight lines intersects with another of said sight lines for said pair of electro-optical sensors having overlapping field of views and an observation time for said three dimensional x,y,z coordinates wherein each of said digital computers within said grid generate said three dimensional X,Y,Z coordinates;

(j) transmitting said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to a central processor;

(k) correlating said three dimensional X,Y,Z coordinates generated by each of said digital computers within said grid to generate a velocity vector which discriminates missile trajectory from infrared emissions in proximity to said missile, wherein a Kalman filter generates said velocity vector which discriminates said missile trajectory from said infrared emissions in proximity to said missile;

(l) identifying which of said aircraft on the flight path at said airport are target aircraft of said missile; and

(m) sending a dispense countermeasure signal to said target aircraft, wherein said target aircraft upon receiving said dispense countermeasure signal releases a countermeasure comprising an infrared flare to deceive said missile and re-route said missile from said flight path.